Wire Loom Chafing at Conduit Exits
**** Hidden Message ***** <P>COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105<BR>CIVIL AVIATION SAFETY AUTHORITY<BR>SCHEDULE OF AIRWORTHINESS DIRECTIVES<BR>Airbus Industrie A319, A320 and A321 Series Aeroplanes<BR>AD/A320/23<BR>Amdt 2<BR>Wire Loom Chafing at Conduit Exits 2/95<BR>Applicability: All A320 series aircraft without Airbus Industrie Modification 22109 or Airbus<BR>Industrie Service Bulletin A320-24-1045 Revision 3 incorporated.<BR>Requirement: 1. Inspect wires in wiring zone 574 and 674 in accordance Airbus Industrie Service<BR>Bulletin A320-24-1044 Revision 2.<BR>a. For any wire showing signs of chafing or overheating, repair or replace in<BR>accordance with the aircraft Maintenance Manual or Aircraft Wiring Manual.<BR>b. For any wire loom not correctly guided centrally into the conduit end fitting, realign<BR>and protect the loom in accordance with Airbus Industrie Service Bulletin<BR>A320-24-1045 Revision 1, or in accordance with the temporary repair defined<BR>in Airbus Industrie SB A320-24-1044 Revision 2, paragraph 2.B(2)(b).<BR>2. Inspect wires in wing and horizontal stabilizer (except in zones 574 and 674 - refer<BR>Requirement 1) in accordance with Airbus Industrie Service Bulletin<BR>A320-24-1044 Revision 2.<BR>a. For any wire showing signs of chafing or overheating, repair or replace in<BR>accordance with the aircraft Maintenance Manual or Aircraft Wiring Manual.<BR>b. For any wire loom not correctly guided centrally into the conduit end fitting, realign<BR>and protect the loom in accordance with Airbus Industrie SB<BR>A320-24-1045 Revision 1, or in accordance with the temporary repair defined<BR>in Airbus Industrie SB A320-24-1044 Revision 2, paragraph 2.B(6)(b).<BR>3. Inspect wires in the main landing gear bays in accordance with Airbus Industrie<BR>Service Bulletin A320-24-1044 Revision 3.<BR>a. For any wire showing signs of chafing or overheating, repair or replace, before<BR>the next flight, in accordance with the aircraft Maintenance Manual or Aircraft<BR>Wiring Manual.<BR>b. For any wire loom which is in contact with the edge of the conduit end fitting or<BR>which may come in contact with the edge of the conduit end fitting during inflight<BR>vibration, re-align and protect the loom, before the next flight, in<BR>accordance with Airbus Industrie Service Bulletin A320-24-1045 Revision 3, or<BR>in accordance with the temporary repair defined in Airbus Industrie SB<BR>A320-24-1044 Revision 3, paragraph 2.B(6)(b).<BR>Note: DGAC AD 91-182-020(B) R2 dated 7 December 1994 refers.<BR>Compliance: The compliance for Requirements 1 and 2 remain unchanged as follows:<BR>1 - Initially within 450 hours time in service after 26 December 1991 and<BR>thereafter, at intervals not exceeding 450 hours time in service.<BR>COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105<BR>CIVIL AVIATION SAFETY AUTHORITY<BR>SCHEDULE OF AIRWORTHINESS DIRECTIVES<BR>2 - Initially within 1500 hours time in service after 26 December 1991 and<BR>thereafter, at intervals not exceeding 3100 hours time in service.<BR>Requirement 3:<BR>Initially within 1500 hours time in service after 2 February 1995 and thereafter, at<BR>intervals not exceeding 3500 hours time in service.<BR>Compliance with Airbus Industrie SB A320-24-1045 Revision 3 constitutes<BR>terminating action for Requirements 1, 2 and 3. Repeat inspections are only required<BR>if temporary repairs are made in accordance with Airbus Industrie SB A320-24-1044<BR>Revision 2 or 3 instead of permanent repairs in accordance with Airbus Industrie SB<BR>A320-24-1045 Revision 1, 2 or 3 as appropriate.<BR>This amendment becomes effective 2 February 1995.<BR>Background: Compliance is necessary in order to prevent the risk of a short circuit of the engine<BR>fire extinguisher bottle circuitry due to chafing of the wiring. Amendment 1 corrected<BR>reference documentation data, included reference to the DGAC Airworthiness<BR>Directive and aligned the title with that of the DGAC Directive. This amendment<BR>adds the main landing gear area to the inspection requirements and contains minor<BR>editorial changes.</P>
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